Launching rack of low-speed light fixed-wing unmanned aerial vehicle

Abstract

The invention discloses a launcher of a low-speed light fixed-wing unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicle launching, the launcher comprises a low-speed light fixed-wing unmanned aerial vehicle body and a base, and the base is sequentially provided with a first supporting rod, a second supporting rod, a third supporting rod and a fourth supporting rod; the first supporting rod, the second supporting rod, the third supporting rod and the fourth supporting rod are provided with a protruding force storage acceleration guide rail, a curve acceleration guide rail, an arc transition guide rail and a linear take-off guide rail correspondingly, and the ball sliding bases are matched with the curve acceleration guide rail, the arc transition guide rail and the linear take-off guide rail. According to the low-speed light fixed-wing unmanned aerial vehicle launcher, acceleration, diving and attack-angle take-off of the low-speed light fixed-wing unmanned aerial vehicle body can be achieved, the aerodynamic layout of the low-speed light fixed-wing unmanned aerial vehicle body during flight is optimized, flight resistance is reduced, energy loss is reduced, and the launcher is simple in structure, convenient to use and high in practicability. The maintenance is easy.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of unmanned aerial vehicle launching, and in particular to a launching rack for a low-speed light-weight fixed-wing unmanned aerial vehicle. BACKGROUND

[0002] The core value of the low-speed light-weight fixed-wing unmanned aerial vehicle lies in filling the application gap between artificial patrol and large professional unmanned aerial vehicles by virtue of low cost, high endurance and low operation threshold, and the low-altitude flight technology is popularized in the fields of agriculture, forestry, transportation and other livelihood professional fields, focuses on efficiently completing specific scene tasks, and is significant in innovating the industry efficiency, cost and application boundary.

[0003] At present, the low-speed light-weight fixed-wing unmanned aerial vehicle depends on the landing gear for takeoff, but the landing gear of the unmanned aerial vehicle makes the unmanned aerial vehicle bear useless extra weight, breaks the original streamline design of the fuselage, generates extra air resistance, and the increased resistance leads to the consumption of more power of the unmanned aerial vehicle to maintain the speed, especially in the high-speed flight scene (such as the fixed-wing unmanned aerial vehicle), the energy consumption loss is more obvious, and when flying at low altitude or encountering airflow, the protruding landing gear is easy to produce airflow interference, which may cause slight shaking of the fuselage, affect the stability of the aerial photography picture or the accuracy of the sensor data, and therefore a low-speed light-weight fixed-wing unmanned aerial vehicle launching rack is needed to meet the use requirement, simplify the unmanned aerial vehicle launching mechanism and landing device, and reduce the launching cost and launching difficulty. SUMMARY

[0004] The application aims to provide a low-speed light-weight fixed-wing unmanned aerial vehicle launching rack to solve the problems in the background.

[0005] To achieve the above-mentioned purpose, the application provides the following technical scheme: a low-speed light-weight fixed-wing unmanned aerial vehicle launching rack, comprising a low-speed light-weight fixed-wing unmanned aerial vehicle body and a base, characterized in that: a first support rod, a second support rod, a third support rod and a fourth support rod are sequentially installed on the base, a convex force storage acceleration guide rail, a curved acceleration guide rail, an arc transition guide rail and a straight takeoff guide rail are respectively installed on the first support rod, the second support rod, the third support rod and the fourth support rod, a ball slide is sleeved and connected on the convex force storage acceleration guide rail in a sliding mode, the ball slide is matched with the curved acceleration guide rail, the arc transition guide rail and the straight takeoff guide rail, and the ball slide is detachably installed at the bottom of the low-speed light-weight fixed-wing unmanned aerial vehicle body.

[0006] Preferably, a first mounting block is installed at the bottom end of each of the first support rod, the second support rod, the third support rod and the fourth support rod, and the first mounting block is fixed on the bottom of the base through a first screw.

[0007] Preferably, the other end of the second support rod and the third support rod is provided with a second curved mounting block, the other end of the fourth support rod is provided with a third mounting block, the second curved mounting block is fixed on the bottom of the curved acceleration guide rail and the arc transition guide rail through a second screw, and the third mounting block is fixed on the bottom of the straight take-off guide rail through a third screw.

[0008] Preferably, the straight acceleration guide rail is provided with a guide rail protrusion, the curved acceleration guide rail is generated by using a cubic spline curve function, the angle between the straight take-off guide rail and the horizontal plane ranges from 3° to 10°, the longitudinal height between the straight acceleration guide rail and the base ranges from 1.5 m to 3 m, and the transverse length of the curved acceleration guide rail ranges from 2 m to 5 m.

[0009] Preferably, the low-speed light-weight fixed-wing unmanned aerial vehicle body is provided with an insertion block at the bottom, the ball slide is provided with an insertion sleeve, the insertion block is inserted into the insertion sleeve, a clamping groove is formed in the insertion block, and a clamping rod is slidably arranged in the insertion sleeve and clamped in the clamping groove.

[0010] Preferably, a spring is arranged on the clamping rod, and the other end of the spring is arranged on the outer wall of the insertion sleeve.

[0011] Preferably, a limiting groove is formed in the insertion sleeve and the clamping groove, and a limiting block is arranged on one side of the clamping rod and slidably arranged in the limiting groove.

[0012] Preferably, a strip-shaped supporting block is arranged on the insertion sleeve, a retaining rod is inserted into the strip-shaped supporting block, a retaining sleeve is arranged on the clamping rod, and the retaining rod is inserted into the retaining sleeve.

[0013] Preferably, a first magnetic attraction block is arranged in the retaining sleeve, and a second magnetic attraction block is arranged at the end of the retaining rod, and the first magnetic attraction block and the second magnetic attraction block are attracted to each other.

[0014] The low-speed light-weight fixed-wing unmanned aerial vehicle body can enter the curved acceleration guide rail through the protrusion force storage acceleration guide rail, dive downward and accelerate, enter the straight take-off guide rail under the transition effect of the arc transition guide rail, take off at a certain angle of attack with the horizontal plane, and then directly take off and ascend under the action of the straight take-off guide rail, without the aid of a landing gear, so that the aerodynamic layout of the low-speed light-weight fixed-wing unmanned aerial vehicle body during flight is optimized, flight resistance is reduced, energy loss is reduced, the launching frame structure is simple, and maintenance is easy.

[0015] The low-speed light-weight fixed-wing unmanned aerial vehicle body can enter the curved acceleration guide rail through the protrusion force storage acceleration guide rail, dive downward and accelerate, enter the straight take-off guide rail under the transition effect of the arc transition guide rail, take off at a certain angle of attack with the horizontal plane, and then directly take off and ascend under the action of the straight take-off guide rail, without the aid of a landing gear, so that the aerodynamic layout of the low-speed light-weight fixed-wing unmanned aerial vehicle body during flight is optimized, flight resistance is reduced, energy loss is reduced, the launching frame structure is simple, and maintenance is easy.

[0016] The present application directly inserts the plug block into the plug sleeve, when the end of the clamping rod coincides with the clamping groove, the clamping rod is inserted into the clamping groove under the reset action of the spring, the fixing connection of the ball slide and the low-speed light fixed-wing unmanned aerial vehicle body can be quickly realized, the clamping rod is pulled outward, and the end of the clamping rod is separated from the clamping groove, and the other clamping rod symmetrically arranged is also operated to be released, and then the low-speed light fixed-wing unmanned aerial vehicle body is directly pulled out upward, so that the ball slide and the low-speed light fixed-wing unmanned aerial vehicle body can be disassembled, and the operation is more convenient. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 A perspective structural schematic view of a launching rack of a low-speed light fixed-wing unmanned aerial vehicle is provided for the present application;

[0018] Figure 2 A side view structural schematic view of a launching rack of a low-speed light fixed-wing unmanned aerial vehicle is provided for the present application;

[0019] Figure 3 A top view structural schematic view of a launching rack of a low-speed light fixed-wing unmanned aerial vehicle is provided for the present application;

[0020] Figure 4 A structural schematic view of a spring, a clamping rod and the like of a launching rack of a low-speed light fixed-wing unmanned aerial vehicle is provided for the present application;

[0021] Figure 5 A structural schematic view of a plug block, a plug sleeve and the like of a launching rack of a low-speed light fixed-wing unmanned aerial vehicle is provided for the present application;

[0022] Figure 6 A structural schematic view of part A of a launching rack of a low-speed light fixed-wing unmanned aerial vehicle is provided for the present application;

[0023] Figure 7 A structural schematic view of a guide rail of a launching rack of a low-speed light fixed-wing unmanned aerial vehicle is provided for the present application.

[0024] In the drawing: 1, low-speed light fixed-wing unmanned aerial vehicle body; 2, base; 3, first support rod; 4, second support rod; 5, third support rod; 6, fourth support rod; 7, convex force storage acceleration guide rail; 8, curved acceleration guide rail; 9, arc transition guide rail; 10, straight take-off guide rail; 11, ball slide; 12, first mounting block; 13, second curved mounting block; 14, third mounting block; 15, guide rail convex; 16, plug block; 17, plug sleeve; 18, clamping groove; 19, clamping rod; 20, spring; 21, limiting block; 22, limiting groove; 23, strip-shaped supporting block; 24, retaining rod; 25, retaining sleeve; 26, first magnetic attraction block; 27, second magnetic attraction block. DETAILED DESCRIPTION

[0025] Clearly, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", and the like are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined with "first", "second" and the like can explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise stated, the meaning of "a plurality of" is two or more.

[0026] Embodiments:

[0027] As Figures 1-6As shown, the embodiment provides a launching rack for low-speed light fixed-wing unmanned aerial vehicle, comprising a low-speed light fixed-wing unmanned aerial vehicle body 1 and a base 2, the base 2 is sequentially provided with a first support rod 3, a second support rod 4, a third support rod 5 and a fourth support rod 6, the first support rod 3, the second support rod 4, the third support rod 5 and the fourth support rod 6 are respectively provided with a convex force storage acceleration guide rail 7, a curved acceleration guide rail 8, an arc transition guide rail 9 and a straight take-off guide rail 10, the convex force storage acceleration guide rail 7 is slidably sleeved with a ball slide 11, the ball slide 11 is adapted to the curved acceleration guide rail 8, the arc transition guide rail 9 and the straight take-off guide rail 10, the ball slide 11 is detachably installed at the bottom of the low-speed light fixed-wing unmanned aerial vehicle body 1, and the convex force storage acceleration guide rail 7 is provided with a guide rail convex 15; the launching rack is placed at a suitable position in advance, and then the ball slide 11 is pushed into the convex force storage acceleration guide rail 7 through the port of the convex force storage acceleration guide rail 7. Then the ball slide 11 is fixedly connected with the low-speed light fixed-wing unmanned aerial vehicle body 1, and an operator can remotely control the low-speed light fixed-wing unmanned aerial vehicle body 1 to advance, and the ball slide 11 will first pass through the guide rail convex 15 in the process of advancing of the low-speed light fixed-wing unmanned aerial vehicle body 1, so that the starting speed of the low-speed light fixed-wing unmanned aerial vehicle body 1 can be improved. Then the low-speed light fixed-wing unmanned aerial vehicle body 1 enters the curved acceleration guide rail 8 through the convex force storage acceleration guide rail 7 to dive downward and accelerate, and enters the straight take-off guide rail 10 under the transition effect of the arc transition guide rail 9, the straight take-off guide rail 10 has a take-off attack angle with the horizontal plane, and then the low-speed light fixed-wing unmanned aerial vehicle body 1 with relatively high speed is directly taken off and ascends under the action of the straight take-off guide rail 10, without the aid of a landing gear for take-off, the aerodynamic layout of the low-speed light fixed-wing unmanned aerial vehicle body 1 during flight is optimized, the flight resistance is reduced, the energy loss is reduced, the launching rack structure is simple, and the launching rack is easy to maintain.

[0028] In order to fix the first support rod 3, the second support rod 4, the third support rod 5 and the fourth support rod 6 at the bottom of the base 2, the first support rod 3, the second support rod 4, the third support rod 5 and the fourth support rod 6 are respectively provided with a first mounting block 12, and the first mounting block 12 is fixed at the bottom of the base 2 through a first screw.

[0029] In order to realize one-to-one correspondence installation and fixation of the first support rod 3, the second support rod 4, the third support rod 5, the fourth support rod 6, the convex force storage acceleration guide rail 7, the curved acceleration guide rail 8, the arc transition guide rail 9 and the straight take-off guide rail 10. The other end of the second support rod 4 and the third support rod 5 is provided with a second curved mounting block 13, and the other end of the fourth support rod 6 is provided with a third mounting block 14. The second curved mounting block 13 is fixed at the bottom of the curved acceleration guide rail 8 and the arc transition guide rail 9 through a second screw, and the third mounting block 14 is fixed at the bottom of the straight take-off guide rail 10 through a third screw. The second curved mounting block 13 can be fixed at the bottom of the curved acceleration guide rail 8 and the arc transition guide rail 9 through a second fixing bolt, so as to fix the second support rod 4 and the third support rod 5 at the bottom of the curved acceleration guide rail 8 and the arc transition guide rail 9 respectively. The third mounting block 14 can be fixed at the bottom of the straight take-off guide rail 10 through a third screw, so as to fix the fourth support rod 6 at the bottom of the straight take-off guide rail 10. It should be noted that the first support rod 3 is provided with a first mounting block 12 at both upper and lower ends, and the other end of the first mounting block 12 is also fixed at the bottom of the convex force storage acceleration guide rail 7 through a first screw.

[0030] In order to provide a take-off attack angle and a certain acceleration space. The convex force storage acceleration guide rail 7 is provided with a guide rail convex 15, the curved acceleration guide rail 8 is generated by using a cubic spline curve function, the angle between the straight take-off guide rail 10 and the horizontal plane is in the range of 3° to 10°, the longitudinal height between the convex force storage acceleration guide rail 7 and the base 2 is in the range of 1.5m to 3m, and the transverse length of the curved acceleration guide rail 8 is in the range of 2m to 5m. The height and length range of the curved acceleration guide rail 8 can provide sufficient acceleration space for the low-speed light fixed-wing unmanned aerial vehicle body 1. The angle between the straight take-off guide rail 10 and the horizontal plane in the range of 3° to 10° can provide a certain take-off attack angle for the flight of the low-speed light fixed-wing unmanned aerial vehicle body 1, and help the low-speed light fixed-wing unmanned aerial vehicle body 1 take off and ascend.

[0031] In order to quickly realize the installation and disassembly of the low-speed light fixed-wing unmanned aerial vehicle body 1 and the ball slide 11. The low-speed light fixed-wing unmanned aerial vehicle body 1 is provided with an insertion block 16 at the bottom, the ball slide 11 is provided with an insertion sleeve 17, the insertion block 16 is inserted into the insertion sleeve 17, a clamping groove 18 is formed in the insertion block 16, a clamping rod 19 is slidably installed in the insertion sleeve 17, the clamping rod 19 is clamped in the clamping groove 18, a spring 20 is installed on the clamping rod 19, and the other end of the spring 20 is installed on the outer wall of the insertion sleeve 17; the insertion block 16 is directly inserted into the insertion sleeve 17, the end of the clamping rod 19 is triangular, when the insertion block 16 is inserted into the insertion sleeve 17, the insertion block 16 will extrude the triangular inclined surface, and then extrude the clamping rod 19 to slide away from the insertion sleeve 17, at this time the spring 20 will also be compressed, when the end of the clamping rod 19 coincides with the clamping groove 18, the clamping rod 19 will be inserted into the clamping groove 18 under the reset action of the spring 20, at this time the fixed connection of the ball slide 11 and the low-speed light fixed-wing unmanned aerial vehicle body 1 can be quickly realized, the clamping rod 19 is pulled outward, and the end of the clamping rod 19 will fall out of the clamping groove 18, the other clamping rod 19 arranged symmetrically is also operated to be released, and then the low-speed light fixed-wing unmanned aerial vehicle body 1 is directly pulled out upward to complete the disassembly of the ball slide 11 and the low-speed light fixed-wing unmanned aerial vehicle body 1.

[0032] In order to avoid the clamping rod 19 being pulled out, the insertion sleeve 17 and the clamping groove 18 are provided with a limiting groove 22, one side of the clamping rod 19 is provided with a limiting block 21, and the limiting block 21 is slidably installed in the limiting groove 22; the clamping rod 19 is pulled outward, and the limiting block 21 enters the insertion sleeve 17 and abuts against the inner wall of the limiting groove 22, so that the clamping rod 19 can be prevented from being pulled out.

[0033] In order to install a strip-shaped supporting block 23 on the insertion sleeve 17, a retaining rod 24 is inserted into the strip-shaped supporting block 23, a retaining sleeve 25 is installed on the clamping rod 19, the retaining rod 24 is inserted into the retaining sleeve 25, a first magnetic block 26 is installed in the retaining sleeve 25, a second magnetic block 27 is installed at the end of the retaining rod 24, and the first magnetic block 26 and the second magnetic block 27 are attracted to each other; the retaining rod 24 is inserted into the retaining sleeve 25, the first magnetic block 26 is attracted to the second magnetic block 27, the retaining rod 24 can be prevented from falling out of the retaining sleeve 25, and the state that the clamping rod 19 is separated from the clamping groove 18 can be maintained.

[0034] Working principle: in use, the launcher is placed in the right position in advance, and then the ball slide 11 is pushed into the convex force storage acceleration guide rail 7 through the port of the convex force storage acceleration guide rail 7. Then directly insert the plug 16 into the plug sleeve 17, the end of the clamping rod 19 is triangular, when the plug 16 is inserted into the plug sleeve 17, the plug 16 will extrude the triangular slope, and then extrude the clamping rod 19 to slide away from the plug sleeve 17, at this time the spring 20 will also be compressed, when the end of the clamping rod 19 coincides with the clamping groove 18, the clamping rod 19 will be inserted into the clamping groove 18 under the reset action of the spring 20, at this time the fixed connection of the ball slide 11 and the low-speed light fixed-wing unmanned aerial vehicle body 1 can be quickly realized. The operator can remotely control the low-speed light fixed-wing unmanned aerial vehicle body 1 to move forward. The low-speed light fixed-wing unmanned aerial vehicle body 1 starts to slide in the convex force storage acceleration guide rail 7 section rotating propeller, when encountering guide rail convex 15, the propeller improves the rotating speed to overcome the resistance of guide rail convex 15, and then stores large thrust for the low-speed light fixed-wing unmanned aerial vehicle body 1, under the action of large thrust, the low-speed light fixed-wing unmanned aerial vehicle body 1 overcomes the guide rail convex 15, accelerates down through the curve guide rail 8 to the lowest point of the guide rail, and smoothly slides to the straight line take-off guide rail 10 through the arc transition guide rail 9. The straight line take-off guide rail 10 provides optimal lift angle of attack for the low-speed light fixed-wing unmanned aerial vehicle body 1, combined with the large take-off speed obtained by the large thrust of the low-speed light fixed-wing unmanned aerial vehicle body 1, the low-speed light fixed-wing unmanned aerial vehicle body 1 can take off smoothly. It does not need to take off with the help of landing gear, optimizes the aerodynamic layout of the low-speed light fixed-wing unmanned aerial vehicle body 1 in flight, reduces the flight resistance and energy loss, and the launcher structure is simple and easy to maintain. After the low-speed light fixed-wing unmanned aerial vehicle body 1 lands, pull the clamping rod 19 outward, and make the limiting block 21 enter the plug sleeve 17 and abut against the inner wall of the limiting groove 22, at this time the end of the clamping rod 19 will fall off from the clamping groove 18, the retaining sleeve 25 will correspond to the end of the retaining rod 24, then insert the retaining rod 24 into the retaining sleeve 25, the first magnetic block 26 will be attracted to the second magnetic block 27, which can prevent the retaining rod 24 from falling off from the retaining sleeve 25, and can keep the state that the clamping rod 19 is separated from the clamping groove 18. Similarly, the other clamping rod 19 arranged symmetrically is also operated to be released, and then the low-speed light fixed-wing unmanned aerial vehicle body 1 is directly pulled out upward to complete the disassembly of the ball slide 11 and the low-speed light fixed-wing unmanned aerial vehicle body 1, which is convenient to operate and use.

[0035] The above is only the preferred specific embodiment of the present application, but the protection scope of the present application is not limited to this. Any skilled person in the art can make equivalent replacement or change according to the technical scheme and the inventive concept of the present application within the technical range disclosed by the present application, which should be covered within the protection scope of the present application.

Claims

1. A launching rack of a low-speed light fixed-wing unmanned aerial vehicle, comprising a low-speed light fixed-wing unmanned aerial vehicle body (1) and a base (2), characterized in that: The base (2) is sequentially provided with a first support rod (3), a second support rod (4), a third support rod (5) and a fourth support rod (6), the first support rod (3), the second support rod (4), the third support rod (5) and the fourth support rod (6) are respectively provided with a convex force storage acceleration guide rail (7), a curved acceleration guide rail (8), an arc transition guide rail (9) and a straight take-off guide rail (10), the convex force storage acceleration guide rail (7) is slidably sleeved with a ball slide (11), the ball slide (11) is matched with the curved acceleration guide rail (8), the arc transition guide rail (9) and the straight take-off guide rail (10), and the ball slide (11) is tightly mounted at the bottom of the low-speed light-weight fixed-wing unmanned aerial vehicle body (1).

2. The launching rack of a low-speed light-weight fixed-wing unmanned aerial vehicle according to claim 1, characterized in that: The first support rod (3), the second support rod (4), the third support rod (5) and the fourth support rod (6) are all provided with a first mounting block (12) at the bottom end, and the first mounting block (12) is fixed on the bottom of the base (2) through a first screw.

3. The launching rack of claim 1, wherein: The second support rod (4) and the third support rod (5) are provided with a second curved mounting block (13) at the other end, the fourth support rod (6) is provided with a third mounting block (14) at the other end, the second curved mounting block (13) is fixed on the bottom of the curved acceleration guide rail (8) and the arc transition guide rail (9) through a second screw, and the third mounting block (14) is fixed on the bottom of the straight take-off guide rail (10) through a third screw.

4. The launching rack of claim 1, wherein: The convex force storage acceleration guide rail (7) is provided with a guide rail convex (15), the curved acceleration guide rail (8) is generated by using a cubic spline curve function, the included angle between the straight take-off guide rail (10) and the horizontal plane ranges from 3° to 10°, the longitudinal height between the convex force storage acceleration guide rail (7) and the base (2) ranges from 1m to 3m, and the transverse length of the curved acceleration guide rail (8) ranges from 2m to 5m.

5. The launching rack of a low-speed light-weight fixed-wing unmanned aerial vehicle according to claim 1, characterized in that: The low-speed light-weight fixed-wing unmanned aerial vehicle body (1) is provided with an insertion block (16) at the bottom, the ball slide (11) is provided with an insertion sleeve (17), the insertion block (16) is inserted into the insertion sleeve (17), the insertion block (16) is provided with a clamping groove (18), the insertion sleeve (17) is slidably provided with a clamping rod (19), and the clamping rod (19) is clamped in the clamping groove (18).

6. The launching rack of a low-speed light-weight fixed-wing unmanned aerial vehicle according to claim 5, characterized in that: The clamping rod (19) is provided with a spring (20), and the other end of the spring (20) is mounted on the outer wall of the insertion sleeve (17).

7. The launching rack of a low-speed light-weight fixed-wing unmanned aerial vehicle according to claim 6, characterized in that: The insertion sleeve (17) and the clamping groove (18) are provided with a limiting groove (22), one side of the clamping rod (19) is provided with a limiting block (21), and the limiting block (21) is slidably mounted in the limiting groove (22).

8. The launching rack of a low-speed light-weight fixed-wing unmanned aerial vehicle according to claim 7, characterized in that: The insertion sleeve (17) is provided with a strip-shaped supporting block (23), the strip-shaped supporting block (23) is inserted with a retaining rod (24), the clamping rod (19) is provided with a retaining sleeve (25), and the retaining rod (24) is inserted into the retaining sleeve (25).

9. The launching rack of claim 7, wherein: A first magnetic block (26) is installed in the retaining sleeve (25), and a second magnetic block (27) is installed at the end of the retaining rod (24), and the first magnetic block (26) and the second magnetic block (27) are attracted to each other.

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